Aluminum and Carbon Fiber Reinforced Polymer Composite Material Comparative Strength Analysis of a Structural Part in F-16 Fighter Aircraft Landing Gear

Abstract

In this study, the geometric structure, weight and boundary conditions of the aluminum alloy main landing gear FS 34.180 structural part currently used in F-16 fighter aircraft are determined. Finite element (FE) analysis is performed considering the forces that the existing part is exposed to in four different scenarios with Ansys Workbench software. Then, a FE model of the same part is created from carbon fiber reinforced polymer (CFRP) composite material. The loading conditions applied in the four scenario are also applied to the new CFRP composite material model. Equivalent stress, equivalent total strain, maximum shear stress and total deformation values in the models created with both materials are calculated.
 The results obtained for both materials are compared. As a result of the comparison, it is observed that there is a decrease of approximately 0.8% in the equivalent stress, 12% in the equivalent total strain, 0.7% in the maximum shear stress and 11.8% in the total deformation values for the same loading and boundary conditions. In addition, the total mass of the part is reduced from 31.17 kg to 20.77 kg, which corresponds to a reduction of 33.37%. 
 This development is expected to reduce the weight of the aircraft as well as extend the fatigue life and maintenance period.